CN109305375A - A kind of twin-fuselage aircraft - Google Patents
A kind of twin-fuselage aircraft Download PDFInfo
- Publication number
- CN109305375A CN109305375A CN201811272337.2A CN201811272337A CN109305375A CN 109305375 A CN109305375 A CN 109305375A CN 201811272337 A CN201811272337 A CN 201811272337A CN 109305375 A CN109305375 A CN 109305375A
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- CN
- China
- Prior art keywords
- fuselage
- twin
- engine
- aircraft
- wing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/16—Aircraft characterised by the type or position of power plant of jet type
- B64D27/18—Aircraft characterised by the type or position of power plant of jet type within or attached to wing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses a kind of twin-fuselage aircrafts, including two fuselages, wing and empennage, described two fuselages to be connected as one by wing, and described two afterbodies are provided with empennage, is provided with engine at left and right sides of each fuselage.The twin-fuselage aircraft, both store Combinations mounting space demand had been can satisfy, it can reduce airframe structure weight simultaneously and reduce interference drag, arrange that the twin-fuselage aircraft of four and the above engine has higher economy than current wing, and yawing caused by asymmetrical thrust when can reduce single-shot parking, it reduces aircraft yaw and controls cost.
Description
Technical field
The invention belongs to aircraft layout designs fields, and in particular to a kind of twin-fuselage aircraft.
Background technique
Have developed two twin-fuselage aircraft for aerial dispensing task, white knight No. 2 and stratosphere in the world at present
Emit Stratolaunch.This kind of aircraft generally has two fuselages in left and right and spacing is larger, the wing among two fuselages
Lower section carry spaceship, sky penetrate the plug-in missile such as rocket.The layout of this twin fuselage both ensure that large sized object carry
Space requirement, and make the stress of the aircraft or so before dispensing and after launching of the heavy weight carrying object positioned at the aircraft plane of symmetry flat
Weighing apparatus is aerial carry platform more satisfactory at present.
It is this kind of at present to consider that engine is arranged under the fuselage outer side wing of left and right by store Combinations space requirement because of aircraft.
Since twin stops the too big unacceptable problem of yaw control cost there are single-shot, these engines be all made of four and
The above engine, such as white knight No. 2 are hung under the wing of left and right fuselage outer side using four fanjets, stratosphere transmitting
Stratolaunch uses six fanjet hangings under the wing of left and right fuselage outer side.Although this distribution engine
Solve the problems, such as that single-shot parking yaw control cost is too big in double publication offices, but so multiple-motor bring is because of engine
Nacelle and the increase hung and generate construction weight are also apparent.It is dry between engine and fuselage and engine to guarantee
Interference resistance power within the acceptable range, must protect between inboard engine and fuselage, between outboard engine and inboard engine
A certain distance is demonstrate,proved, this causes outermost engine apart from the aircraft plane of symmetry apart from larger.To guarantee that single-shot failure aircraft can
Control, it is necessary to increase vertical fin area, so as to cause fuselage weight increase.When the increase of resistance and weight leads to this kind of Aircraft and boat
The reduction of journey, while economic index is also deteriorated.
Summary of the invention
In view of the above-mentioned problems, the present invention provides a kind of twin-fuselage aircrafts, store Combinations mounting space demand both can satisfy,
It can reduce airframe structure weight simultaneously and reduce resistance, than the twin-fuselage aircraft that current wing arranges four and the above engine
With higher economy, and yawing caused by asymmetrical thrust when single-shot stops can be reduced, reduce aircraft yaw
Control cost.
The technical problem to be solved in the present invention is realized using following technical scheme:
A kind of twin-fuselage aircraft, including two fuselages, wing and empennage, described two fuselages are connected as one by wing
Body, described two afterbodies are provided with empennage, are provided with engine at left and right sides of each fuselage.
Four engines by being arranged in the left and right sides of two fuselages, two machines by twin-fuselage aircraft of the invention
The distance between engine on the outside of body is less than distance of engine arrangement when on wing between two engines of outermost, because
Yawing caused by asymmetrical thrust reduces when this single engine is stopped, fuselage in the case where identical shipping-direction stability
The area of vertical fin reduces, to mitigate the construction weight of twin fuselage.Secondly, starting by engine arrangement at left and right sides of fuselage
The engine nacelle of machine can partially borrow airframe structure during installation, mitigate the construction weight of twin-fuselage aircraft.Finally, due to
Four engines are placed in the left and right sides of twin fuselage, between the engine of single fuselage two sides due to the partition of fuselage do not generate it is dry
Interference resistance power, farther out, interference drag is small for the distance between two fuselages, it therefore reduces the interference drag of twin-fuselage aircraft.Interference
The reduction of resistance and weight extends the endurance and voyage of twin-fuselage aircraft, improves the economy of such aircraft.
Preferably, engine is provided at left and right sides of each waist.
Using above-mentioned preferred embodiment, when four engines are placed in the left and right sides of waist, since afterbody becomes
Narrow, influence of the engine tail nozzle High Temperature Jet to fuselage is smaller, while influence of the weight of engine to full machine center of gravity is can
In the range of receiving.Engine nacelle can partially borrow airframe structure, reduce aircraft cross-sectional area, reduce full machine construction weight
With reduction resistance.
Preferably, engine is provided at left and right sides of each front fuselage.
Using above-mentioned preferred embodiment, when four engines are placed in the left and right sides of twin fuselage front end, since engine is pacified
Loaded on front fuselage, cause the center of gravity of aircraft is opposite to move forward, to guarantee that certain longitudinal stability remaining reduces horizontal tail area, thus
The construction weight for alleviating aircraft, reduces resistance.
Preferably, the empennage includes the vertical fin being placed on each afterbody, is arranged between two vertical fins
There is horizontal tail.
End plate effect is mutually formed using above-mentioned preferred embodiment, between horizontal tail and vertical fin, pneumatic efficiency is higher.
Preferably, horizontal tail is provided between two vertical fin tops.
Using above-mentioned preferred embodiment, when horizontal tail is arranged between vertical fin top, the pneumatic efficiency highest of horizontal tail and vertical fin.
Preferably, the empennage includes the vertical fin being placed on each afterbody, is provided on each vertical fin
Horizontal tail.
End plate effect is mutually formed using above-mentioned preferred embodiment, between horizontal tail and vertical fin, pneumatic efficiency is high.
Preferably, each vertical fin top is provided with horizontal tail.
Using above-mentioned preferred embodiment, when the pneumatic efficiency of horizontal tail and vertical fin at each vertical fin top is arranged in horizontal tail
Highest.
Preferably, each back body is provided with abdomeinal fin.It is provided with or without according to the requirement of course stability
Abdomeinal fin.
Preferably, the engine is any one in fanjet or turbojet engine.
Detailed description of the invention
Fig. 1 engine is placed in the structural schematic diagram at left and right sides of waist；
Fig. 2 engine is placed in the structural schematic diagram at left and right sides of front fuselage.
Marked in the figure: 1- fuselage；2- wing；3- horizontal tail；4- vertical fin；5- engine；6- abdomeinal fin.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawing and specific implementation
The present invention is described in detail for example.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, not
For limiting the present invention.
Embodiment 1
As shown in Fig.1 and Fig.2, a kind of twin-fuselage aircraft, including two fuselages 1, wing 2 and empennage, described two fuselages 1
It is connected as one by wing 2, described two 1 tail portions of fuselage are provided with empennage, and the left and right sides of each fuselage 1 is respectively provided with
There is engine 5.Two fuselages 1 are connected as one by wing 2, the position of wing 2 according to the positioning of the position of centre of gravity of fuselage 1 and
It determines, as shown in Fig.1 and Fig.2, since engine 5 is placed in the different location of fuselage 1, the position of centre of gravity of aircraft is caused to change, thus
The position that wing 2 is in fuselage 1 changes.The left and right sides of each fuselage 1 is respectively provided with engine 5, i.e. the twin fuselage
Aircraft is provided with four engines 5, and four engines are placed in the left and right sides of twin fuselage, then two engines 5 are placed in two machines
The outside of body 1, two engines 5 are placed in the inside of two fuselages 1, and the layout in this way of engine 5 is so that be placed in two fuselages, 1 outside
The distance between engine be less than distance of engine arrangement when on wing between two engines of outermost, therefore when single
When platform engine cut-off, yawing caused by asymmetrical thrust reduces, and fuselage 1 hangs down in the case where identical shipping-direction stability
The area of tail 4 reduces.Secondly as engine nacelle part is overlapped with fuselage, therefore when installing engine nacelle, it can portion
Divide and borrow 1 structure of fuselage, to mitigate the construction weight of twin-fuselage aircraft.Finally, due to which four engines 5 are placed in twin fuselage
The left and right sides, since the partition of fuselage 1 does not generate interference drag between the engine 5 of single 1 two sides of fuselage, two are located at fuselage
Farther out due to distance, interference drag is small, therefore, overall reduces the interference of twin-fuselage aircraft for the engine 5 of 1 inside
Resistance.Therefore, the reduction of the reduction of interference drag and construction weight improves double so that the endurance of such aircraft and voyage increase
The economy of airframe.In addition, there also is provided operation rudder face on each aerofoil, increasing can also be arranged on wing as needed
Device, spoiler etc. are risen, the wheeled sliding aircraft for running landing further includes undercarriage, and manned aircraft is in left fuselage or right fuselage head
Portion there also is provided cockpit, these are the common knowledge of those skilled in the art, no longer carry out detailed repeat herein.
Embodiment 2
As shown in Figure 1, on the basis of embodiment 1, the left and right sides at each 1 middle part of fuselage is provided with engine 5.
When engine 5 is placed in the left and right sides at 1 middle part of fuselage, since afterbody narrows, engine tail nozzle High Temperature Jet pair
The influence of fuselage is smaller, while influence of the weight of engine to full machine center of gravity is within the acceptable range.Engine nacelle can
Partially to borrow airframe structure, reduce aircraft cross-sectional area, reduce full machine construction weight and reduces resistance.In the present embodiment,
The content that it is not described is same as the previously described embodiments, and details are not described herein again.
Embodiment 3
As shown in Fig. 2, on the basis of embodiment 1, being provided with engine at left and right sides of each 1 front end of fuselage.
Since engine 5 is installed on 1 front end of fuselage, cause the center of gravity of aircraft is opposite to move forward, and the center of gravity of aircraft is hundred before aircraft focus
/ several to more than ten Average aerodynamic strings, therefore, the Forward of the center of gravity of aircraft will lead to the focus Forward of aircraft, and focal position and flat
3 area of tail is positively correlated, therefore focus moves forward, and 3 area of horizontal tail reduces, to alleviate the construction weight of aircraft, reduces resistance.
In the present embodiment, other contents not described are same as the previously described embodiments, and details are not described herein again.
Embodiment 4
As shown in Figure 1, on the basis of embodiment 1, the empennage includes the vertical fin being placed on each 1 tail portion of the fuselage
4, horizontal tail 3 is provided between two vertical fins 4.1 secondary horizontal tail 3 is arranged between two vertical fins 4, and horizontal tail 3 may be mounted at vertical
Any position between tail 4.Such empennage layout, so that mutually forming end plate effect between horizontal tail 3 and vertical fin 4, pneumatically
It is more efficient.In the present embodiment, other contents not described are same as the previously described embodiments, and details are not described herein again.
Embodiment 5
As shown in Figure 1, being provided with horizontal tail 3 between two 4 tops of vertical fin on the basis of embodiment 4.In this tail
In the layout type of the wing, when the top between vertical fin 4 is arranged in horizontal tail 3, the pneumatic efficiency highest of horizontal tail 3 and vertical fin 4.This reality
It applies in example, other contents not described are same as the previously described embodiments, and details are not described herein again.
Embodiment 6
As shown in Fig. 2, on the basis of embodiment 1, the empennage includes the vertical fin being placed on each 1 tail portion of the fuselage
4, horizontal tail 3 is provided on each vertical fin 4.Horizontal tail 3 can be set on any position of each vertical fin 4, two are arranged altogether and puts down
Tail 3, two horizontal tails 3 are placed in same level.The embodiment is another layout of empennage, can equally make 3 He of horizontal tail
End plate effect is mutually formed between vertical fin 4, pneumatic efficiency is higher.In the present embodiment, other contents not described and above-mentioned implementation
Example is identical, and details are not described herein again.
Embodiment 7
As shown in Fig. 2, each vertical fin top is provided with horizontal tail on the basis of embodiment 6.It is laid out in this empennage
Mode in, when two horizontal tails 3 are arranged at the top of two vertical fins 4, the pneumatic of horizontal tail 3 and vertical fin 4 can be made
Efficiency highest.In the present embodiment, other contents not described are same as the previously described embodiments, and details are not described herein again.
Embodiment 8
As shown in Figure 1, on the basis of embodiment 1, each 1 rear end of fuselage is provided with abdomeinal fin 6.It is stable according to course
Property require abdomeinal fin 6 can be set, abdomeinal fin 6 is mounted on to the rear end of each fuselage 1, altogether be arranged two abdomeinal fins 6, can also not
Abdomeinal fin 6 is set.In the present embodiment, other contents not described are same as the previously described embodiments, and details are not described herein again.
Embodiment 9
On the basis of embodiment 1-8, the engine 5 is any one in fanjet or turbojet engine.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, it is noted that all
Made any modifications, equivalent replacements, and improvements etc. within the spirit and principles in the present invention should be included in guarantor of the invention
Within the scope of shield.
Claims (9)
1. a kind of twin-fuselage aircraft, including two fuselages, wing and empennage, described two fuselages are connected as one by wing,
Empennage is provided on described two afterbodies, which is characterized in that is provided with engine at left and right sides of each fuselage.
2. a kind of twin-fuselage aircraft according to claim 1, which is characterized in that the left and right sides of each waist
It is provided with engine.
3. a kind of twin-fuselage aircraft according to claim 1, which is characterized in that the left and right sides of each front fuselage
It is provided with engine.
4. a kind of twin-fuselage aircraft according to claim 1, which is characterized in that the empennage includes being placed in each machine
Vertical fin on body tail portion is provided with horizontal tail between two vertical fins.
5. a kind of twin-fuselage aircraft according to claim 4, which is characterized in that be provided between two vertical fin tops
Horizontal tail.
6. a kind of twin-fuselage aircraft according to claim 1, which is characterized in that the empennage includes being placed in each machine
Vertical fin on body tail portion is provided with horizontal tail on each vertical fin.
7. a kind of twin-fuselage aircraft according to claim 6, which is characterized in that each vertical fin top is provided with flat
Tail.
8. a kind of twin-fuselage aircraft according to claim 1, which is characterized in that each back body is provided with abdomen
Fin.
9. a kind of twin-fuselage aircraft according to claim 1-8, which is characterized in that the engine is turbofan hair
Any one in motivation or turbojet engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811272337.2A CN109305375A (en) | 2018-10-29 | 2018-10-29 | A kind of twin-fuselage aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811272337.2A CN109305375A (en) | 2018-10-29 | 2018-10-29 | A kind of twin-fuselage aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109305375A true CN109305375A (en) | 2019-02-05 |
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ID=65222148
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811272337.2A Pending CN109305375A (en) | 2018-10-29 | 2018-10-29 | A kind of twin-fuselage aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109305375A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110228590A (en) * | 2019-06-30 | 2019-09-13 | 郑州航空工业管理学院 | A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane |
| CN111017185A (en) * | 2019-12-19 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Laminar flow technology verification machine |
-
2018
- 2018-10-29 CN CN201811272337.2A patent/CN109305375A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110228590A (en) * | 2019-06-30 | 2019-09-13 | 郑州航空工业管理学院 | A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane |
| CN111017185A (en) * | 2019-12-19 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Laminar flow technology verification machine |
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| PB01 | Publication | ||
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| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Zhang Zhenhua Inventor before: Guo Dong Inventor before: Zhang Qiaoliang Inventor before: Li Jinjie |